AAE450 Senior Spacecraft Design Kate Mitchell - 1 Kate Mitchell Week 6: February 22 nd, 2007 Human Factors – Group Lead HAB & TV Vehicle Groups This Week:
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Kate Mitchell - 1
AAE450 Senior Spacecraft Design
Kate MitchellWeek 6: February 22nd, 2007
Human Factors – Group LeadHAB & TV Vehicle Groups
This Week: Updated Mass/Power/Volume for HAB & TV, HAB Layout
Kate Mitchell - 2
AAE450 Senior Spacecraft Design
HAB & TV
Mass (m t) Volum e (m 3) Pow er (kW)
HAB Totals (em pty) (per HAB) 36.76 301.6 20.82
HAB 1 Totals (w / Consum ables) 77.13 301.6 20.82
HAB 2 Totals (w / Consum ables) 94.49 301.6 20.82
Mass (mt) Volume (m3) Power (kW)
Totals 68.74 175.9 19.86
Totals for each TV Crew Cab
Totals for each HAB Crew Cab
Mass (mt) Volume (m3) Power (kW)
Totals 22.11 73.60 -
• Requirements– HAB: sized for crew of 6, fits 4 nominally, and must be able to support 8 in an emergency– TV: must be able to support crew of 4 for 3 years (in case of free return)
• Capabilities– HABs are stocked with consumables to support first 2 crews
– All water and O2 to support HAB crews is produced on Mars beginning in 6th synodic period (3rd crew)
– TVs contain enough consumables to re-supply HABs with food and other misc. consumables
Totals for Re-supply Launches to TV (x5)
*Total masses for HAB and TV include consumables, crew accommodations, radiation shielding, and LSS.
Kate Mitchell - 3
AAE450 Senior Spacecraft Design
HAB Layout
Kate Mitchell - 3
3 m Consumables Storage/Plumbing/Piping
3 m Crew Living Quarters
Side
Nominal Configuration (4 crew)Section Volume (m
3)
Crew Common Area 96.4(SPE Shelter) 12.0(Other Common Space) 57.16Crew Private Area (4 crew) 54.4(Private quarters per crew) 13.6Consumables Storage 150.8Total Habitable Volume 150.8
Total Volume 301.6
Section Volume (m3)
Crew Common Area 69.2(SPE Shelter) 12.0(Other Common Space) 57.16Crew Private Area (6 crew) 81.6(Private quarters per crew) 13.6Consumables Storage 150.8Total Habitable Volume 150.8
Total Volume 301.6
Contingency Configuration (6 crew)
4 m
Crew Common Area
1.25 m
Top
Crew Private Area
2 m
2 m
SPE Shelter
Retractable Walls
Kate Mitchell - 4
AAE450 Senior Spacecraft Design
Back-up Slides
Kate Mitchell - 5
AAE450 Senior Spacecraft Design
TV Layout
Kate Mitchell - 5
4 m
Consumables Storage 1 (40%) (Food, Miscellaneous Consumables)
Crew Common Area (60%)
2 m
Top
3.5 m
4 m
2 m
1.0 m
SideConsumables Storage 2 (Water, Life Support Systems, Plumbing/Piping)
Section Volume (m3)
Crew Common Area 56.5
Crew Private Area 44.0
(SPE Shelter) 8.0
(Crew Rooms) 36.0
Consumables Storage 75.4
(Consumables Storage 1 (food and misc. consumables)) 52.8
(Consumables Storage 2 (water, life support systems, and plumbing/piping)) 22.6
Total Habitable Volume 108.5
Total Volume 175.9
Consumables Storage
SPE Shelter
Private Quarters
Outer Walls
Kate Mitchell - 6
AAE450 Senior Spacecraft Design
Habitable Volume Comparison
*TV and HAB unobstructed habitable volume falls b/w performance and optimal values recommended in the NASA ALS Baselines Document.
Comparison of Unobstructed Habitable Volume
NASA Advanced Life Support Baselines Recommended Assumptions for Unobstructed Habitable Volume [1]
Case Volume (m 3) Volume (m 3/person) Time in Volume
ME 117 (20' x 30' x 10' estimate) 169.9 6.07 3 hours
TV Crew Cab 47.28 11.82 170 days (each w ay)
HAB Crew Cab (6 crew ) 73.95 12.32 782 days
HAB Crew Cab (4 crew ) 73.95 18.49 1329 days
Mission Units Tolerable Performance Optimal
Mars Habitat m3/person 5.1 9.91 18.41
Mars Transit Phase m3/person 5.1 9.91 18.41
*Breakdown of HAB and TV Habitable Volume attached
Kate Mitchell - 7
AAE450 Senior Spacecraft Design
Totals BreakdownComponent Mass (mt) Volume (m3) Power (kW)
Consumables (HAB1) 40.38 101.38 -
Consumables (HAB2) 57.73 101.38
Crew Accommodations 19.38 - 16.55
Water Recycling System 0.40 1.60 0.24
Atmospheric Supply System 5.87 20.39 0.56
Private Quarters - 90.00 -
Crew Common Area - 90.00 -
Radiation Shielding 4.98 - -
HAB Totals (empty) (per HAB) 36.76 301.6 20.82
HAB 1 Totals (w/ Consumables) 77.13 301.6 20.82
HAB 2 Totals (w/ Consumables) 94.49 301.6 20.82
Component Mass (mt) Volume (m3) Power (kW)
Consumables 28.53 52.62 -
Crew Accommodations 12.23 - 16.29
Water Recycling System 0.20 0.80 0.24
Atmospheric Supply System 1.13 8.05 0.28
Private Quarters - 44.00 -
Crew Common Area - 56.50 -
Radiation Shielding 15.20 - -
Totals 68.74 175.90 19.86
HAB
TV
Kate Mitchell - 8
AAE450 Senior Spacecraft Design
Water Consumption
Max Water on board (at one time) 25022.624 kg
Water Storage Volume 25.02 m3
• 1st table* is a breakdown of all components of crew water consumption
• 2nd table shows max water that will need to be stored in TV and HAB and as well as its volume
Parameter Mass Units
Crew Drinks 2 kg/p/dTotal Metabolic and Related Consumption 2 kg/p/dUrinal Flush 0.5 kg/p/dOral Hygiene 0.37 kg/p/dHand Wash 4.08 kg/p/dShower 2.72 kg/p/dLaundry 12.47 kg/p/dDish Wash 5.44 kg/p/dFood Processing and Prep 1.9 kg/p/dTotal Hygiene Consumption 27.48 kg/p/dDaily Water Consumption (per person) 29.48 kg/p/dTotal Daily Water Consumption 117.92 kg/d
Crew Consumption of Water per day[1]
*Crew water consumption table first used in presentation on 1/25/07
HAB
Max Water on board (at one time) 13,030 kg
Water Storage Volume 13.03 m3
TV
Kate Mitchell - 9
AAE450 Senior Spacecraft Design
Water Launched
Launch Mass (kg) Volume (m3)
Each Transfer Vehicle (x4) 13,030 13.03
Each Resupply (x5) 13,030 13.03
Total Water Launched 117,270 117.27
TV
Launch Mass (kg) Volume (m3)
HAB1 18,561 18.56
HAB2 25,023 25.02
Total Water Launched 59,267 59.27
HAB
*Water calculations done in MATLAB code
HAB Code: attached to week 2 presentation (HAB_consume.m – 3 pages
TV Code: attached to week 4 presentation (TV_consume.m) – 3 pages
Kate Mitchell - 10
AAE450 Senior Spacecraft Design
Food Consumption
Launch Mass (kg) Volume (m3)
HAB1 14,389 50.05
HAB2 19,430 67.58
Parameter Mass Mass Units Volume Volume Units
Food 2.3 kg/p/d 0.008 m3/p/d
Crew Consumption of Food per day• 1st table shows mass and
volume of food consumed per crew member per day
• 2nd table shows mass and volume of food to be launched in each TV as well as re-supply ships
• 3rd table shows mass and volume of food to be launched in each HAB
*Food calculations done in MATLAB code
HAB Code: attached to week 2 presentation (HAB_consume.m) – 3 pages
TV Code: attached to week 4 presentation (TV_consume.m) – 3 pages
Launch Mass (kg) Volume (m3)
Each Transfer Vehicle (x4) 12,100 41.28
Each Resupply (x5) 12,100 41.28
Food Launched in TV
Food Launched in HAB
Kate Mitchell - 11
AAE450 Senior Spacecraft Design
Atmospheric Supply Values
Launch Mass O2 (kg) Mass N2 (kg) Mass H2 (kg) Gas Sum per Launch (kg)
Each Transfer Vehicle (x4) 710 640 400 1750
Each Resupply (x5) 710 640 400 1750
Total Launched 6390 5760 3600 15750
Total Gases Launched (kg) 15,750
Launch Mass O2 (kg) Mass N2 (kg) Mass H2 (kg) Gas Sum per Launch (kg)
HAB1 1715.04 3245.68 568.73 5529.45
HAB2 3099.31 6994.06 768 10861.37
Total Launched 4814.35 10239.74 1336.73 16390.82
Total gases per Launch as well as total IMLEO through entire architecture*
*Atmospheric supply calculations done in MATLAB code
HAB Code: attached to week 2 presentation (HAB_consume.m – 3 pages
TV Code: attached to week 4 presentation (TV_consume.m) – 3 pages
TV
Total Gases Launched (kg) 16390.82
HAB
Kate Mitchell - 12
AAE450 Senior Spacecraft Design
Atmospheric Supply System Schematic
H2 Tank
422 2
Sabatier Reac
2
t r
4
o
H OCO H CH CH4
22 2
Electrolysis Machine
H 2 2H O O
H2O
H2
O2
CO2
(from atmosphere in vehicle)
HAB or TV
Condenser
Martian Atmosphere (HAB) or Vacuum Environment (TV)
Kate Mitchell - 13
AAE450 Senior Spacecraft Design
Atmospheric Supply Calculations*
• Atmospheric pressure: 101 kPa
• Partial pressures: 80 kPa N2
21 kPa O2
• Volume of 1 mole of gas (101 kPa and 298 K): 0.02445 m3/mole
• Mass of gas needed to fill the pressurized volume:
• Mass of gas needed assuming 0.14% mass per day leakage rate:
• Using Sabatier/electrolysis reaction:
• Oxygen consumption rate: 0.835 kg/p/d
• Total oxygen consumed by crew:
3
Partial Pressure 1kg 1Mass of Ambient Gas (kg) *Molar Mass (g/mol)* * *Pressurized Volume
Total Pressure 1000g 0.02445
mol
m
Days
Mass of Ambient Gas (kg)Mass of Needed Gas (kg) =
(1-0.0014)
2 2 4 2CO H CH O
2 2Total O consumed = O consumption rate (kg/person/day)*person*days
*Slide first used in presentation on 1/25/07
Kate Mitchell - 14
AAE450 Senior Spacecraft Design
2 2Total CO produced (kg) = CO production rate (kg/person/day)*person*days
22 2 2
2 2
1 kmol O1 reclaimed (kg) = Total CO produced (kg)* * *O molar mass (kg/kmol)
CO molar mass (kg/kmol) 1 kmol COO
2 2 2 2 tankage (kg) = needed (kg)*O tankage value (kg tank/kg O )O O
2 2 2 2 tankage (kg) = N needed (kg)*N tankage value (kg tank/kg N )N
33
1Tank volume (m ) = Gas needed (kg)*
Gas density (kg/m )
Find Mass of O2 Tank (using O2 tankage value of 0.364 kg tank/kg O2 [1] ):
Find Mass of N2 Tank (using N2 tankage value of 0.556 kg tank/kg N2 [1] ):
Volume of tanks (Assuming density of gases to be 1440 kg/m3):
Total oxygen reclaimed:
Total carbon dioxide produced by crew:
CO2 production rate: 1 kg/p/d
Atmospheric Supply Calculations*
*Slide first used in presentation on 1/25/07
Kate Mitchell - 15
AAE450 Senior Spacecraft Design
H2 Tank Calculations
2
2 22 2
2 2
2 mol O H Molar Mass1H Mass, ( ) ( Reclaimed w/ LSS)
O Molar Mass 1 mol H 1LHM kg O
Mass of H2 needed by Atmospheric Supply System:
H2 Tank Volume and Mass Calculations:
2
2
LH3
LH
3
2
MTank Volume, ( ) =
Tank Radius, ( ) = 43
Tank Thickness, ( ) = 2
(where is the LH Internal Pressure ( 151,700 ),and is the tensile yield strength
of the tank structure (
y
y
y
V m
Vr m
Prt m
P P Pa
r
s
s
s 6
3 3 3
tank Al
3 3Al
520 10 ))
4 4Wall Volume, ( ) = ( )
3 3Tank Mass, ( ) =
(where =2.59 10 / )
wall
wall
x Pa
V m r r t
M kg V
x kg m
r
r
*H2 Tank Calculations for the HAB and TV are attached
Kate Mitchell - 16
AAE450 Senior Spacecraft Design
Life Support Systems
Components Mass (kg/p) Mass (kg) Volume (m3/p) Volume (m3) Power (kW-h/p) Power (kW)
Sabatier Reactor (2x) [5] 76 304 0.14 0.56 0.02 0.08
O2 Tankage [1] - 260 - 0.5 - -
N2 Tankage [1] - 355 - 0.45 - -
Contaminant Control System [5] 20 80 0.15 0.6 0.05 0.2
Redundant Parts (10% system hardware) - 40 0.2 - -
Totals 1039 2.31 0.28
Water Recycling System Mass Units Mass (kg) Volume Units Volume (m3) Power Units Power (kW)
Vapor Compression Distillation (VCD) (2x)[5] 50 kg/p 400 0.2 m3/p 1.6 0.06 kW/p 0.48
TV Water Recycling System
TV CO2 Removal/Atmospheric Supply System
Water Recycling System Mass Units Mass (kg) Volume Units Volume (m3) Power Units Power (kW)
Vapor Compression Distillation (VCD) (2x)[5] 50 kg/p 200 0.2 m3/p 0.8 0.06 kW/p 0.24
HAB Water Recycling System
HAB CO2 Removal/Atmospheric Supply SystemComponents Mass (kg/p) Mass (kg) Volume (m3/p) Volume (m3) Power (kW-h/p) Power (kW)
Sabatier Reactor (2x) [5] 76 608 0.14 1.12 0.02 0.16
O2 Tankage [1] - 1128.15 - 2.15 - -
N2 Tankage [1] - 3888.7 - 4.86 - -
H2 Tankage - 12.29 - 10.83 - -
Contaminant Control System [5] 20 160 0.15 1.2 0.05 0.4
Redundant Parts (10% system hardware) - 76.8 0.232 - -
Totals 5873.94 20.392 0.56
Kate Mitchell - 17
AAE450 Senior Spacecraft Design
TV Radiation Shielding
Material Thickness (cm) Density (g/cm3) Arial Density (g/cm2)
Aluminum 5 2.78 13.9
Polyethelyne 16 1 16
Totals 12 - 29.9
Arial Density (g/cm2) 29.9
Shielded Surface Area (m2) 28
Total Shield Mass (kg) 8372
Material Thickness (cm) Density (g/cm3) Arial Density (g/cm2)
Aluminum 1 2.78 2.78
Polyethelyne 2 1 2
Totals 12 - 4.78
Arial Density (g/cm2) 4.78
Shielded Surface Area (m2) 142.8
Total Shield Mass (kg) 6826
Total Mass of Radiation Shielding (mt) 15.20
SPE Shelter Shielding
Entire Crew Compartment Shielding
*TV Radiation shielding tables first used in presentation on 2/5/07
Kate Mitchell - 18
AAE450 Senior Spacecraft Design
HAB Radiation Shielding
Arial Density (g/cm2) 15.56
Shielded Surface Area (m2) 32
Total Shield Mass (kg) 4979.2
Material Thickness (cm) Density (g/cm3) Arial Density (g/cm2)
Aluminum 2 2.78 5.56
Polyethelyne 10 1 10
Totals 12 - 15.56
SPE Shelter Shielding
Total Mass of Radiation Shielding (mt) 4.98
Entire Crew Compartment Shielding
None (16 g/cm2 shielding provided by Martian Atmosphere is
sufficient)
Kate Mitchell - 19
AAE450 Senior Spacecraft Design
References
[1] Hanford, Anthony J., ed. NASA Johnson Space Center. Advanced Life Support Baseline Values and Assumptions Document. Aug. 2004. http://ston.jsc.nasa.gov/collections/TRS/_techrep/CR-2004-208941.pdf
[2] Landau, Dr. Damon F., “Strategies for the Substained Human Exploration of Mars.” Thesis Submitted to the Faculty of Purdue University, Dec. 2006.
[3] Niziolek, Paul, Project Legend - Final Report - Appendix. April 2005. p. 478-480.
[4] Reed, Ronald D., and Gary R. Coulter. "Physiology of Spaceflight." Human Spaceflight: Mission Analysis and Design. Ed. Wiley J. Larson and Linda K. Prank. New York: McGraw-Hill, 1999. 113-115.
[5] Stilwell, Don, Ramzy Boutros, and Janis H. Connolly. "Crew Accomodations." Human Spaceflight: Mission Analysis and Design. Ed. Wiley J. Larson and Linda K. Prank. New York: McGraw-Hill, 1999. 575-606.
[6] Tribble, Alan C. "The Space Environment: Hazards and Effects." Human Spaceflight: Mission Analysis and Design. Ed. Wiley J. Larson and Linda K. Prank. New York: McGraw-Hill, 1999. 65-73.
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